Aircraft grounding system

ABSTRACT

Liquid dispensing assemblies including adhesive anchoring assemblies configured to adhere to a support surface external to a device such as a vehicle. An air vehicle includes (a) a fluid adhesive container assembly detachably attached to the air vehicle, wherein the fluid adhesive container assembly comprises: (i) an adhesive container comprising fluid adhesive; and (ii) one or more fibers, wherein the one or more fibers are configured, or a brush of fibers, or a fabric of fibers, is configured to conduct the fluid adhesive and to structurally support an adhesive bond between the one or more fibers and a surface; and (b) means for dispensing the fluid adhesive from the fluid adhesive container, to the one or more fibers.

CROSS-REFERENCE TO RELATED APPLICATION

This application is a continuation of U.S. patent application Ser. No.14/149,730 filed Jan. 7, 2014, which is a continuation of U.S. patentapplication Ser. No. 13/478,560 filed May 23, 2012, which is acontinuation of International Application No. PCT/US2010/057984, filedNov. 24, 2010, and claims priority to and the benefit of U.S.Provisional Patent Application Ser. No. 61/264,220, filed Nov. 24, 2009,all of which are hereby incorporated herein by reference in theirentirety for all purposes.

FEDERALLY SPONSORED RESEARCH

The invention was made with Government support under HR0011-07-C-0075awarded by DARPA. The Government has certain rights in the invention.

TECHNICAL FIELD

Embodiments pertain to deployable adhesive anchoring systems andparticularly to adhesive anchoring systems for aircraft.

BACKGROUND

An unmanned aerial vehicle (UAV) may land or alight on a surface onwhich the UAV may slide due to gravity or other forces such asaerodynamic forces. A UAV may land or alight on, or position itselfproximate to, a surface on which the UAV may be tasked to apply aliquid-based pigment to a target region of the surface. The use ofbeacons, antenna elements, and/or instrumentation packets may requirerapid affixing of such devices to surfaces or available supportstructures.

SUMMARY

Embodiments include liquid dispensing assemblies including adhesiveanchoring assemblies configured to adhere to a support surface externalto a vehicle. For example, an assembly may comprise: (a) an assemblyhousing comprising a fluid reservoir; (b) a resilient member disposedproximate to the assembly housing; and (c) a fluid conduit configured topierce the reservoir responsive to a decompression of the resilientmember. In some embodiments, the fluid may be an adhesive. In someembodiments, the assembly further comprises a liquid infusible brush.

In still other embodiments, the fluid reservoir may be a liquid adhesivereservoir and the liquid infusible brush may be a liquid adhesiveinfusible brush. The fluid conduit may be configured to pierce thereservoir via a frusto-conical tip.

Embodiments may include a system comprising a vehicle and an adhesiveanchoring assembly configured to adhere to a support surface external tothe vehicle. For example, a portion of the adhesive anchoring assemblymay be detachable. A portion of the adhesive anchoring assembly may beconfigured to rotate into a deployed position. The adhesive anchoringassembly may comprise a liquid adhesive reservoir and a liquid adhesiveinfusible brush.

Embodiments may include methods of attachment and detachable attachment.For example, a method of adhesive bonding may comprise: (a) providing anadhesive in a positive pressure reservoir having positive pressure abovelocal atmospheric pressure to force a portion of the adhesive along aconduit to an application surface under local atmospheric pressure; and(b) releasing a resiliently loaded conduit having a tip configured topierce the reservoir when the resiliently loaded conduit is unloaded.The exemplary reservoir may be detachably attached to a supportstructure, e.g., an air vehicle fuselage, and the method may furthercomprise detaching the reservoir from the support structure. Anotherexemplary method of detachably anchoring a device via adhesive bondingmay comprise: (a) detachably attaching a positive pressure reservoir toa device, e.g., an air vehicle, an transmitter, or an illuminator,wherein the positive pressure reservoir contains an adhesive, andwherein the reservoir containing the adhesive has positive pressureabove local atmosphere to force a portion of the adhesive along aconduit to an application surface under local atmospheric pressure; (b)releasing a resiliently loaded conduit having a tip configured to piercethe reservoir when the resiliently loaded conduit is unloaded; and (c)deploying the application surface to a surface of a support structure,e.g., a target anchoring surface. The exemplary reservoir may be fixedlyattached to the support structure via the application surface connectedto the conduit, itself connected to the detachable reservoir, and themethod may further comprise detaching the reservoir from the device.

BRIEF DESCRIPTION OF THE DRAWINGS

Embodiments are illustrated by way of example and not limitation in thefigures of the accompanying drawings, and in which:

FIGS. 1A, 1B, and 1C illustrate an exemplary Vertical Take-Off andLanding (VTOL) use of an embodiment of the present invention;

FIGS. 2A, 2B, and 2C illustrate an exemplary fixed-wing use of anembodiment of the present invention;

FIGS. 3A and 3B illustrate an exemplary arrangement of elements of anassembly embodiment of the present invention;

FIGS. 3C and 3D illustrate exemplary detachments of portions of theelements of assembly embodiments of the present invention;

FIG. 4 illustrates an assembly embodiment of the present invention;

FIGS. 5A, 5B, and 5C illustrate an assembly embodiment of the presentinvention;

FIGS. 6A and 6B illustrate another assembly embodiment of the presentinvention;

FIGS. 7A and 7B illustrate yet another assembly embodiment of thepresent invention;

FIGS. 8A, 8B, 8C, 8D and 8E illustrate stowing and rotational deploymentof an embodiment of the present invention;

FIG. 9 illustrates an example of a dispensing case embodiment within acavity of an aircraft fuselage;

FIG. 10 illustrates another embodiment of the adhesive anchoringassembly in a stowed position;

FIG. 11 illustrates another embodiment of the adhesive anchoringassembly in a deployed position;

FIG. 12A illustrates another embodiment of the adhesive anchoringassembly showing a direction of rotation into a deployed position;

FIG. 12B illustrates the embodiment of the adhesive anchoring assemblyof FIG. 12A showing a deployed position where the brush portion is incontact with a surface;

FIG. 13A illustrates another embodiment of the adhesive anchoringassembly in a stowed position;

FIG. 13B illustrates the embodiment of the adhesive anchoring assemblyin a stowed position of FIG. 13A with the conduit position to allow flowof a liquid adhesive to the brush portion;

FIG. 13C illustrates the embodiment of the adhesive anchoring assemblyof FIG. 13B showing a direction of rotation into a deployed position;

FIG. 14A illustrates in a cross-sectional view another embodiment of thepresent invention;

FIG. 14B illustrates in a cross-sectional view a portion of theembodiment of FIG. 14A;

FIG. 15 illustrates a side view of the embodiment of the presentinvention of FIG. 14A;

FIG. 16 illustrates a side view of a deflected embodiment of the presentinvention depicted in FIG. 15;

FIG. 17 illustrates a cross-sectional view of the deflected embodimentof the present invention depicted in FIG. 16;

FIG. 18 illustrates in a cross-sectional view another embodiment of thepresent invention;

FIGS. 19A and 19B illustrate an exemplary clasp;

FIG. 20 illustrates in cross-sectional view the embodiment depicted inFIG. 18 further comprising a clasp;

FIG. 21 illustrates in a perspective view an exemplary frusto-conicaltip of an embodiment of the present invention;

FIG. 22 illustrates in an elevational side view an exemplaryfrusto-conical tip of an embodiment of the present invention;

FIG. 23 illustrates in a top view an exemplary frusto-conical tip of anembodiment of the present invention;

FIG. 24 illustrates in an elevational front view an exemplaryfrusto-conical tip of an embodiment of the present invention;

FIG. 25 illustrates in a cross-sectional view another embodiment of thepresent invention;

FIG. 26 illustrates a cross-sectional view of the deflected embodimentof the present invention depicted in FIG. 25;

FIG. 27 illustrates a cross-sectional view of a portion of a deflectedembodiment of the present invention depicted in FIG. 25;

FIG. 28 illustrates a cross-sectional view of a portion of theembodiment of the present invention depicted in FIG. 25; and

FIG. 29 illustrates a cross-sectional view of a portion of a deflectedembodiment of the present invention depicted in FIG. 25.

DETAILED DESCRIPTION

Reference is made to the drawings that illustrate exemplary embodimentsof the present invention. FIGS. 1A, 1B, and 1C illustrate an exemplaryembodiment of the present invention where, in FIG. 1A, a verticaltakeoff and landing craft (VTOL) aircraft 110 such as a helicopterdescends to a landing surface 120. A contact member 130 is extended inFIG. 1B from the aircraft 110 until the contact member makes contactwith a portion of the landing surface 120. The contact member 130,either before or after making contact with the portion of the landingsurface 120, may be infused or otherwise provided with an adhesiveliquid causing the contact member 130 to bond with the portion of thelanding surface 120. An attachment member 140 connects the contactmember 130 to the aircraft 110. Accordingly, the aircraft 110 may beadhesively anchored to the landing surface 120. The attachment member140 may detachably attach to either the aircraft 110, the contact member130, or both. In particular, the attachment member 140 may detach fromthe aircraft 110 or the contact member 130, and the aircraft 110, beingno longer anchored to the landing surface 120, may resume flight asshown in FIG. 1C. Similarly, FIGS. 2A, 2B, and 2C illustrate anexemplary embodiment of the present invention where, in FIG. 2A, a fixedwing aircraft 210 descends to a landing surface 120. In FIG. 2B acontact member 130 is extended from the aircraft and contacts a portionof the landing surface 120. The contact member 130 may be detachablyattached from the aircraft 210 and the detached aircraft 210 may free toresume flight as shown in FIG. 2C.

FIG. 3A shows an assembly comprising an aircraft 310 attached to aliquid adhesive reservoir by an attachment_1 320. A channel or conduit330 may be provided between the liquid adhesive reservoir 340 and abrush assembly 350 such as a filament array, bristle array, or an arrayof bundles, strips of fabric, cotton balls, or clumps of cloth. Theliquid adhesive reservoir 340 may be attached by attachment_2 360 to thefilament array 350. Before or after the filament array 350 contacts theanchoring surface 370, the liquid adhesive may flow from the liquidadhesive reservoir 340 to the filament array 350 via the conduit 330 asshown in FIG. 3B. The filament elements of the filament array 350 havingliquid adhesive provide the anchoring surface 370 with bonding areas.Once elements of the filament array 350 have bonded to the anchoringsurface 370, the aircraft may be adhesively anchored to the anchoringsurface 370. To free itself from the anchor provided by the bondedelements of the filament array 350, the aircraft may be detached viarelease of attachment_1 320 as shown in FIG. 3C or release ofattachment_2 360 as shown in FIG. 3D, or combinations thereof.

FIG. 4 shows an assembly comprising a cylinder 410 for containing aliquid adhesive reservoir where the assembly further comprises anattachment joint 420 at a proximal end of the cylinder and an array offilaments 430, bristles, or fabric strips, at the distal end of thecylinder. A channel or conduit may be provided within the cylinder 410between the liquid adhesive reservoir and the filament array 430 forconducting the flow of the liquid adhesive to the filament array, wherethe filament array may be in contact with a surface for anchoring. FIG.4 also shows the assembly may be stowed, prior to deployment, in adispensing case 440.

FIG. 5A shows in cross-section the cylinder 510 having a plunger 511with a shaft 512 piercing a stopper 513. FIG. 5B shows the liquidadhesive 520 may be expressed from the cylinder 510 as the plunger 511moves toward the opening 514. FIG. 5C shows the brush 530 of the distalportion 515 of the cylinder 510 may disperse its fibers or filaments insuch a fashion as to provide contact with uneven surfaces 540. FIG. 6Ashows in cross-section the cylinder 610 having a pointed spring-loadedshaft 611 held in place by a pin 612. FIG. 6B shows that with the pinremoved, the pointed spear 611 may pierce a seal 613 of the liquidadhesive reservoir, allowing the liquid glue to flow to the bundle ofbristles or filaments 530. FIG. 7A shows the cylinder 710 having athreaded shaft 711 with a threaded seal/stopper 712. A liquid adhesivereservoir 720 is shown disposed between the threaded seal/stopper 712and the brush assembly 530. FIG. 7B shows that a rotation 713 of thethreaded shaft 711 causes the threaded seal 712 to translate toward thedistal end 715 of the cylinder 710, thereby expressing the liquidadhesive 730 from the reservoir 720. FIG. 8A shows in perspective view adispensing case 810 comprising three rotatably and detachably attachedbrush-cylinder systems 821-823. FIG. 8B shows a rotational degree offreedom of a cylinder glue dispensing embodiment 821 of the presentinvention. FIG. 8C shows a dispensing case 810 in a top view with afirst cylinder 821 elevated. FIG. 8D shows in a side view a dispensingcase 810 mounted within a body 820 with the distal brush element 830 ofthe cylinder 821 rotationally brought into contact with a surface 840. Aleg 850 is shown attached to the body 820 providing elevational supportof the body 820 from the contact surface 840. FIG. 8E shows a portion ofthe dispensing case assembly 810 where a drive gear assembly effects 860the rotation of a worm gear 861 causing a threaded shaft 862 to rotate afirst cylinder 821, and if the threaded shaft is further rotated, todisengage the joint of the cylinder 821—leaving the cylinder 821mechanically disconnected from the dispensing case. Further rotation ofthe drive gear causes the next cylinder 822 to rotationally extend. FIG.9 shows a dispensing case 810 disposed on the underside of an aircraft920. Shown also in FIG. 9 are four legs 931-934 extending from the bodyof the aircraft.

FIG. 10 shows an embodiment of the liquid adhesive storage anddeployment assembly 1000 where the liquid adhesive reservoir 1010 andthe conduit and brush assembly portion 1020 are stowed parallel to oneanother. The conduit 1021 has a piercing aperture 1022 disposed on agooseneck conduit 1023. The conduit and brush assembly portion 1020 maybe rotated, e.g., by a released spring-loaded rotating joint assembly,into and piercing a seal 1011 of a liquid adhesive reservoir 1010. Thecontents 1012 of the reservoir 1010, or glue packet may be underpressure via a clamp spring 1030. The contents 1012 of the reservoir1010 may be under pressure, e.g., via a clamp via a gas bladder, wheresuch embodiments may be applicable in environments with nominalatmospheric pressure variation. FIG. 11 shows the conduit and brushassembly 1020 having rotated approximately 90 degrees causing thepiercing aperture 1022 to pierce the seal 1011 of the liquid adhesivereservoir 1010 and set up a path for the adhesive to flow to thebristles or filaments of the brush 1140. FIG. 12A shows the liquidadhesive reservoir 1010 and the conduit and brush assembly portion 1020are stowed parallel to one another within a portion of an aircraftfuselage 1200 having fixed pedestal legs 1211, 1212, and that theconduit and brush assembly portion 1020 may rotate to a positionorthogonal and extending from the fuselage 1200. The conduit and brushassembly portion 1020 may rotate before or after the aircraft lands on acontact surface. FIG. 12B shows an example of the brushes of theassembly in contact with the contact surface 1220. FIG. 13A showsanother embodiment of the liquid adhesive storage and deploymentassembly 1300 having a spring-loaded conduit and brush assembly portion1320 having a loaded spring 1321 that may be held in place by a pin 1322and solenoid or servo actuated 1323. The brush assembly may be furtherbundled via a brush filament conduit such as a silicone conduit having adistal end, for example, a brush tip. For some embodiments, the brushfilament conduit may be comprised of a wrapped KEVLAR tube. FIG. 13Bshows that with the pin 1322 retracted, the conduit and brush assembly1320 has been thrust into and has penetrated the liquid adhesivereservoir seal 1011. FIG. 13C shows the liquid adhesive reservoir andthe conduit and brush assembly portion of the embodiment 1301 of FIG.13B rotated to extend the brush portion 1350 out of the fuselage 1200and onto a contact surface 1220. Rather than pivoting about a point ofrotation, the assembly may be configured so that a portion of theassembly rotates or bends to deploy the brush assembly.

FIG. 14A shows in a cross-sectional view another embodiment of theliquid adhesive storage and deployment assembly 1400 where a flexiblelineal conduit 1421 has a piercing aperture 1422 proximate to the liquidadhesive reservoir 1410. A collar member 1480 is shown external to abrush filament conduit 1451. The brush filament bundle 1450 is shownextending from the end of the brush filament conduit 1451 distal fromthe liquid adhesive reservoir 1410. FIG. 14B shows in a cross-sectionalview the distal portion of the assembly of FIG. 14A where the flexiblelineal conduit 1421 terminates before the end of the brush filamentconduit 1451 and where a portion of a spring wire 1481, as an example ofa resilient member, is in contact with, or fixed to, the collar 1480.FIG. 15 shows in a side view the spring wire 1481 in contact with thecollar 1480, where the collar is disposed about the brush filamentconduit 1451. Another portion of the spring 1583 is disposed on amounting sleeve or mounting case 1590 as seen in FIG. 15. The springwire 1481 is compressed and held in place by a pin 1582. FIG. 16 showsin a side view the spring wire 1481 is in a restored, i.e.,uncompressed, position and the brush filament conduit 1451 is deflectedthereby reorienting the brush filament bundle 1450. FIG. 17 illustratesin a cross-sectional view the deflection of the brush filament conduit1451 which places pressure in the distal end portion of the flexiblelineal conduit 1421, a pressure that works to drive the piercingaperture 1422 into the liquid adhesive reservoir 1410 via a pierced seal1711. Accordingly, the assembly 1700 is shown in a deployed state havinga brush filament bundle 1450 receiving liquid from the reservoir 1410and positioned for application to an exemplary surface 1701. FIG. 18illustrates in a cross-sectional view a portion of an exemplary assembly1800 where an adhesive reservoir 1810 may comprise a threaded portion1811 for secure assembly. FIG. 19A illustrates in a front view areservoir spring clasp 1900. FIG. 19B illustrates in a side view areservoir spring clasp 1900. FIG. 20 illustrates in a cross-sectionalview a portion of an exemplary assembly 1800 where an adhesive reservoir1810 may have a reservoir spring clasp 1900 apply pressure to thereservoir 1810.

FIG. 21 illustrates in a perspective view an exemplary frusto-conicaltip 2100 of an embodiment of the present invention that may be disposedon an end of an adhesive flow conduit 1421. The exemplary frusto-conicaltip 2100 is depicted as including a cylindrical attachment band portion2110. The exemplary frusto-conical tip 2100 may be embodied havingopposing teardrop-shaped apertures where a first teardrop-shapedaperture 2120 is shown in FIG. 21 depicted having opposingteardrop-shaped apertures, the narrow portions of the teardrop distalfrom the conduit, the wider portions of the teardrop proximate to thecylindrical band, and where the teardrop-shaped apertures are showndisposed on the conic portion of the tip. FIG. 22 illustrates in anelevational side view an exemplary frusto-conical tip 2100 of anembodiment of the present invention having a teardrop-shaped aperture2120. FIG. 23 illustrates in a top view an exemplary frusto-conical tip2100 of an embodiment of the present invention and depicts the firstteardrop-shaped aperture 2120 opposing a second teardrop-shaped aperture2121. FIG. 24 illustrates in an elevational front view an exemplaryfrusto-conical tip 2100 of an embodiment of the present invention.

FIG. 25 illustrates in a cross-sectional view another embodiment of thepresent invention comprising an adhesive flow conduit 1421 having afrusto-conical tip 2100 proximate to the adhesive reservoir seal 1711.FIG. 26 illustrates a cross-sectional view of the deflected embodimentof the present invention depicted in FIG. 25 where the frusto-conicaltip 2100 is shown piercing the adhesive reservoir seal 1711.

FIG. 27 illustrates a cross-sectional view of a portion of a deflectedembodiment of the present invention depicted in FIG. 25 where thefrusto-conical tip 2100 has pierced the adhesive reservoir seal 1711 andwhere the adhesive of the reservoir flows into the conduit 1421 via theteardrop-shaped apertures 2120, 2121 of the frusto-conical tip 2100.Expanded depictions are shown in FIGS. 28 and 29 where in FIG. 28 isillustrated a cross-sectional view of a portion of the embodiment of thepresent invention depicted in FIG. 25, and where in FIG. 29 isillustrated a cross-sectional view of a portion of a deflectedembodiment of the present invention depicted in FIG. 25.

Accordingly, embodiments of the present invention may provide a systemfor use in temporarily affixing an aircraft to the ground and in whichthe aircraft has a removable gripper, or anchor unit attached to theundercarriage. The anchor or gripper unit has a frame containing threeground-lock tubes. Each tube connects to an actuation system configuredto extend the tube down such that a brush portion at the end of the tubeis pressed against the tube, splaying the brush filaments on the ground.Embodiments of the invention include an adhesive reservoir that may be atube having an inner piston configured to eject an adhesive such as, forexample, a tenacious adhesive type substance, which is stored within thetube, out of the tube and through the brush portion. For example,cyanoacrylate is the generic name for cyanoacrylate-based, fast-actingglues such as methyl-2-cyanoacrylate, ethyl-2-cyanoacrylate (commonlysold under trade names like The Original Super Glue® and Krazy Glue),n-butyl-cyanoacrylate (used in the veterinary glues Vetbond and LiquiVetand skin glues like Indermil and Histoacryl). 2-octyl cyanoacrylate isthe medical grade glue encountered under various trade names, e.g.SurgiSeal™, FloraSeal™, Dermabond™, and Nexaband™. The liquid adhesivesuch as a cyanoacrylate adhesive binds the plane to the ground once theadhesive dries. To provide the aircraft with stability during windyconditions, the ground point to which the brush attaches may be locateddirectly below the aircraft center of drag, or proximate to thatlocation. The tube actuation system may be configured to release thetube when it is time for the aircraft to be released from the ground.

It is contemplated that various combinations and/or sub-combinations ofthe specific features and aspects of the above embodiments may be madeand still fall within the scope of the invention. Accordingly, it shouldbe understood that various features and aspects of the disclosedembodiments may be combined with or substituted for one another in orderto form varying modes of the disclosed invention. Further it is intendedthat the scope of the present invention herein disclosed by way ofexamples should not be limited by the particular disclosed embodimentsdescribed above.

What is claimed is:
 1. A method comprising: adhering an air vehicle withan adhesive to an external surface; wherein adhering the air vehiclefurther comprises: adhering an adhesive anchoring assembly of the airvehicle, via the adhesive, to an air vehicle landing surface external tothe air vehicle; and wherein adhering the adhesive anchoring assembly ofthe air vehicle further comprises: rotating at least one cylinder of theadhesive anchoring assembly relative to the air vehicle, the at leastone cylinder comprising an attachment joint disposed on one end of theat least one cylinder proximate to the air vehicle and a brush assemblydisposed on a distal end of the at least one cylinder.
 2. The method ofclaim 1 wherein adhering the adhesive anchoring assembly of the airvehicle further comprises: adhering a contact member of the adhesiveanchoring assembly to the air vehicle landing surface, wherein thecontact member is connected to the air vehicle by an attachment member.3. The method of claim 2 further comprising: detaching the attachmentmember from the air vehicle.
 4. The method of claim 2 furthercomprising: detaching the contact member from the attachment member,wherein the attachment member remains connected to the air vehicle. 5.The method of claim 1 wherein the at least one cylinder is rotatedrelative to the air vehicle before the air vehicle has landed on the airvehicle landing surface.
 6. The method of claim 1 wherein the at leastone cylinder is rotated relative to the air vehicle after the airvehicle has landed on the air vehicle landing surface.
 7. The method ofclaim 6 further comprising: conducting the adhesive from a liquidadhesive reservoir to the brush assembly via a fluid conduit disposedbetween the liquid adhesive reservoir and the brush assembly.
 8. Themethod of claim 7 wherein conducting the adhesive further comprises:piercing, by a spear disposed on an end of the fluid conduit, a seal ofthe liquid adhesive reservoir.
 9. The method of claim 7 furthercomprising: infusing the brush assembly with the adhesive, wherein thebrush assembly comprises at least one of: a filament array, a bristlearray, one or more strips of fabric, one or more cotton balls, and oneor more clumps of cloth.
 10. The method of claim 1 further comprising:splaying the brush assembly over the air vehicle landing surface. 11.The method of claim 10 wherein the air vehicle landing surface issubstantially uneven relative to the air vehicle.
 12. The method ofclaim 10 wherein the air vehicle landing surface is proximate to asurface directly below the air vehicle center of drag.
 13. The method ofclaim 10 further comprising: detaching the at least one cylinder fromthe adhesive anchoring assembly at the attachment joint.
 14. The methodof claim 13 further comprising: rotating a second cylinder of theadhesive anchoring assembly relative to the air vehicle, the secondcylinder comprising a second attachment joint disposed on one end of thesecond cylinder proximate to the air vehicle and a second brush assemblydisposed on a distal end of the second cylinder; splaying the secondbrush assembly over a second air vehicle landing surface; conducting asecond adhesive from a second liquid adhesive reservoir to the secondbrush assembly; and infusing the second brush assembly with the secondadhesive, wherein the second brush assembly comprises at least one of: afilament array, a bristle array, one or more strips of fabric, one ormore cotton balls, and one or more clumps of cloth.
 15. The method ofclaim 14 further comprising: detaching the second cylinder from theadhesive anchoring assembly at the attachment joint.
 16. A methodcomprising: adhering an air vehicle with an adhesive to an externalsurface; wherein adhering the air vehicle further comprises: adhering anadhesive anchoring assembly of the air vehicle, via the adhesive, to anair vehicle landing surface external to the air vehicle; and whereinadhering the adhesive anchoring assembly of the air vehicle furthercomprises: releasing a resiliently loaded conduit of the adhesiveanchoring assembly, the resiliently loaded conduit having a speardisposed on an end of the conduit; piercing, by the spear, a liquidadhesive reservoir of the adhesive anchoring assembly having positivepressure above a local atmospheric pressure; conducting, via theconduit, the adhesive to a brush assembly of the adhesive anchoringassembly; and infusing the brush assembly with the adhesive.
 17. Themethod of claim 16 further comprising: detaching a portion of theadhesive anchoring assembly from the air vehicle.
 18. The method ofclaim 17 further comprising: adhering the air vehicle with a secondadhesive to a second external surface.
 19. The method of claim 16wherein adhering the adhesive anchoring assembly of the air vehiclefurther comprises: splaying the brush assembly over the air vehiclelanding surface.
 20. The method of claim 16 wherein the air vehiclelanding surface is at least one of: substantially uneven relative to theair vehicle, and proximate to a surface directly below the air vehiclecenter of drag.